Trajectory planning method for the entire recovery process of the reusable launch vehicle is studied. Firstly, a revised trajectory correction method (RTCM) is proposed to reduce the maximum normal aerodynamic load in the endo-atmosphere unpowered descent phase and improve the vehicle's landing accuracy on the influence of wind field. It consists of two parts, namely moving the ignition point of the vertical landing phase on the horizontal plane and introducing preset steady wind field into trajectory planning. Secondly, a compound trajectory planning method, which combines Particle Swarm Optimization algorithm (PSO) with Polynomial Guidance Law (PGL), is proposed to complete the optimization task of the entire recovery process. Employing PSO algorithm can avoid the complex calculation of additional angle of attack caused by the preset steady wind field in traditional trajectory correction. To overcome the premature convergence of basic PSO, the traditional re-initialization mechanism is improved. Finally, the guidance simulation of two phases greatly affected by wind is accomplished. The effectiveness of the proposed methods is demonstrated with some scenarios and Monte Carlo simulation.

研究了可重复使用运载火箭整个回收过程的弹道规划方法。首先，提出了一种修正的轨迹修正方法（RTCM），以减少大气层内无动力下降阶段的最大法向气动载荷，提高飞行器在风场影响下的着陆精度。它由两部分组成，即在水平面上移动垂直着陆阶段的点火点和将预设的稳定风场引入轨迹规划。其次，提出了一种将粒子群优化算法（PSO）与多项式制导律（PGL）相结合的复合轨迹规划方法来完成整个恢复过程的优化任务。采用PSO算法可以避免传统轨迹修正中由于预设稳定风场而导致的附加迎角计算复杂。为了克服基本粒子群算法的早熟收敛问题，对传统的重新初始化机制进行了改进。最后完成了受风影响较大的两相的制导仿真。通过一些场景和蒙特卡罗模拟证明了所提出方法的有效性。